Gas turbine engine blade outer air seal thermal control system

Abstract

A clearance control system for a gas turbine engine includes a full hoop blade outer air seal carrier ring, a full hoop thermal control ring at least partially contained within the full hoop blade outer air seal blade outer air seal carrier ring to form an interference fit therebetween, and a multiple of blade outer air seals mounted to the full hoop blade outer air seal carrier ring.

What is claimed: 
     
       1. A clearance control system for a gas turbine engine, comprising:
 a full hoop blade outer air seal carrier ring that forms a generally rectilinear compartment; 
 a full hoop thermal control ring at least partially contained within the generally rectilinear compartment of said full hoop blade outer air seal carrier ring, the full hoop blade outer air seal carrier ring is of a slightly smaller diameter than the full hoop thermal control ring to form an interference fit therebetween; and 
 a multiple of blade outer air seals mounted to said full hoop blade outer air seal carrier ring. 
 
     
     
       2. The system as recited in  claim 1 , wherein said interference fit is at assembly. 
     
     
       3. The system as recited in  claim 1 , wherein said interference fit is about 14 mil (0.014 inch; 0.3556 mm) on a radius of a 30 inch (762 mm) diameter full hoop thermal control ring. 
     
     
       4. The system as recited in  claim 1 , wherein said interference fit is between an inner surface of said full hoop blade outer air seal carrier ring and an outer surface of said full hoop thermal control ring. 
     
     
       5. The system as recited in  claim 1 , wherein said multiple of blade outer air seals locally bound a core flowpath through the gas turbine engine. 
     
     
       6. The system as recited in  claim 1 , further comprising a containment ring that interfaces with said full hoop blade outer air seal carrier ring. 
     
     
       7. The system as recited in  claim 6 , wherein said containment ring interfaces with a case of the gas turbine engine. 
     
     
       8. The system as recited in  claim 6 , wherein said containment ring interfaces with a turbine case of the gas turbine engine. 
     
     
       9. The system as recited in  claim 1 , wherein said full hoop blade outer air seal carrier ring includes a main body with an outer wall and an inner wall interconnected by a radially extending wall, said interference fit between an inner surface of said outer wall of said full hoop blade outer air seal carrier ring, and an outer surface of said full hoop thermal control ring. 
     
     
       10. The system as recited in  claim 9 , wherein said full hoop blade outer air seal carrier ring inner wall forms a forward feature and an aft feature that engage said multiple of blade outer air seals. 
     
     
       11. The system as recited in  claim 9 , further comprising an extension on said radially extending wall to facilitate maintaining a relationship of the full hoop thermal control ring within the full hoop blade outer air seal carrier ring. 
     
     
       12. The system as recited in  claim 1 , further comprising a spring located between said full hoop thermal control ring and an inner wall of said full hoop blade outer air seal carrier ring to maintain a bias between said full hoop thermal control ring and said full hoop blade outer air seal carrier ring. 
     
     
       13. A clearance control system for a gas turbine engine, comprising:
 a containment ring; 
 a full hoop blade outer air seal carrier that interfaces with said containment ring; and 
 a full hoop thermal control ring at least partially contained said full hoop blade outer air seal carrier ring, the full hoop blade outer air seal carrier ring is of a slightly smaller diameter than the full hoop thermal control ring to form an interference fit therebetween; and 
 further comprising a cover that encloses a generally rectilinear compartment. 
 
     
     
       14. The system as recited in  claim 13 , further comprising a multiple of blade outer air seals mounted to said full hoop blade outer air seal carrier ring. 
     
     
       15. The system as recited in  claim 13 , wherein said containment ring interfaces with a case of the gas turbine engine. 
     
     
       16. The system as recited in  claim 13 , wherein said interference fit is at assembly between an inner surface of said full hoop blade outer air seal carrier ring and an outer surface of said full hoop thermal control ring. 
     
     
       17. The system as recited in  claim 13 , wherein the cover is formed by the containment ring. 
     
     
       18. The system as recited in  claim 17 , wherein the full hoop thermal control ring includes an axial extension at least partially received in said cover to maintain a relationship therebetween. 
     
     
       19. A method of assembling a clearance control system for a gas turbine engine, comprising:
 assembling a full hoop thermal control ring at least partially within a full hoop blade outer air seal carrier ring, the full hoop blade outer air seal carrier ring is of a slightly smaller diameter than the full hoop thermal control ring to form an interference fit therebetween at assembly; and 
 enclosing the full hoop thermal control ring within a generally rectilinear compartment formed by the full hoop blade outer air seal carrier ring. 
 
     
     
       20. The method as recited in  claim 19 , further comprising: assembling the full hoop blade outer air seal carrier ring to a containment ring.